Airworthiness Directive · Amendment 39-14309 · McDonnell Douglas Model DC-10-10 and DC-10-10F Airplanes; Model DC-10-15 Airplanes; Model DC-10-30 and DC-10-30F (KC-10A and KDC-10) Airplanes; Model DC-10-40 and DC-10-40F Airplanes; Model MD-10-10F and MD-10-30F Airplanes; and Model MD-11 and MD-11F Airplanes
McDonnell Douglas Model DC-10-10 and DC-10-10F Airplanes; Model DC-10-15 Airplanes; Model DC-10-30 and DC-10-30F (KC-10A and KDC-10) Airplanes; Model DC-10-40 and DC-10-40F Airplanes; Model MD-10-10F and MD-10-30F Airplanes; and Model MD-11 and MD-11F Airplanes
This AD applies to the airplanes identified in Table 1 of this AD; certificated in any category.
| McDonnell Douglas— | As identified in— |
|---|---|
| Model DC-10-10 and DC-10-10F airplanes; Model DC-10-15 airplanes; Model DC-10-30 and DC-10-30F (KC-10A and KDC-10) airplanes; Model DC-10-40 and DC-10-40F airplanes; and Model MD-10-10F and MD-10-30F airplanes | Boeing Alert Service Bulletin DC10-27A236, dated February 17, 2005. |
| Model MD-11 and MD-11F airplanes | Boeing Alert Service Bulletin MD11-27A083, dated February 17, 2005. |
The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas transport category airplanes. This AD requires an inspection of the rudder pedal torque tube assembly for cracking; an inspection of the torque tube assembly to determine the thickness of the torque tube wall, if necessary; and replacing the rudder torque tube with a new or serviceable rudder torque tube, if necessary. This AD results from a report of a broken rudder pedal torque tube. We are issuing this AD to prevent failure of a rudder pedal torque tube, which could result in loss of rudder control and nose wheel steering controlled by the rudder pedal, and consequent reduced controllability of the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Within 6 months after the effective date of this AD, do a special detailed eddy current inspection of the rudder pedal torque tube assembly for cracks, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin DC10-27A236, dated February 17, 2005; or Boeing Alert Service Bulletin MD11-27A083, dated February 17, 2005; as applicable. If any crack is found, before further flight, replace the rudder pedal torque tube with a new or serviceable rudder pedal torque tube, in accordance with the applicable service bulletin.
If no cracking is found during the special detailed eddy current inspection required by paragraph (f) of this AD, before further flight, do a special detailed ultrasonic inspection of the rudder pedal torque tube assembly to determine the wall thickness of the rudder pedal torque tube, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin DC10-27A236, dated February 17, 2005; or Boeing Alert Service Bulletin MD11-27A083, dated February 17, 2005; as applicable.
(1) If the wall thickness of the torque tube is within the limits identified as area C in Appendix B of the applicable service bulletin, no further action is required by this AD.
(2) If the wall thickness of the torque tube is within the limits identified as area B in Appendix B of the applicable service bulletin, within 6,000 flight hours after doing the special detailed ultrasonic inspection, replace the torque tube with a new or serviceable torque tube, in accordance with the applicable service bulletin.
(3) If the wall thickness of the torque tube is below the minimum limits, which are identified as area A in Appendix B of the applicable service bulletin, before further flight, replace the torque tube with a new or serviceable torque tube, in accordance with the applicable service bulletin.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
